TG studies of a composite sold rocket propellant based on HTPB-binder

Resumo

Thermal decomposition kinetics of solid rocket propellants based on hydroxyl-terminated poly-butadiene-HTPB binder was studied by applying the Arrhenius and Flynn-Wall-Ozawa's methods. The thermal decomposition data of the propellant samples were analyzed by thermogravimetric analysis (TG/DTG) at different heating rates in the temperature range of 300-1200 K. TG curves showed that the thermal degradation occurred in three main stages regardless of the plasticizer (DOA) raw material, the partial HTPB/IPDI binder and the total ammonium perchlorate decompositions. The kinetic parameters Ea (activation energy) and A (pre-exponential factor) and the compensation parameter (Sp) were determined. The apparent activation energies obtained from different methods showed a very good agreement.

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